Device and method for precise point delivery of cargo for various purposes

Claims

1. A universal cargo multifunctional container for precise point delivery of a payload with the ability to loiter during a controlled flight (hereinafter referred to as the product) is a container consisting of the following sections: a head section of an ogive or similar shape, possibly equipped with special inserts that are transparent in the operating ranges of the guidance and control systems, including control, guidance and monitoring systems using GPS / GLONASS, and may also include a servo drive with a rudder rotation mechanism arm, while the batteries that supply power to the propeller-motor group and the entire control group of the product may be located, depending on the final centering of the product, partially or completely in either the head or the engine compartment, or in the payload compartment;a payload compartment equipped with devices for securing the payload and components, as well as lines passing through the hull, while a cargo hatch is located in the shell of the hull, allowing for the loading and securing of the transported payload; an engine compartment equipped with an electric motor with a pusher propeller providing a thrust force in accordance with the aerodynamic and weight characteristics of the product, wherein the hull of the engine compartment, possibly equipped with air intakes, has a conical or aerodynamic shape, which ensures better air flow, possibly including control elements, including stabilizers, as well as fins located on the hull of the aft compartment, equipped with rudders that can create control moments in pitch, yaw and roll both synchronously and asynchronously;equipped with a monowing for loitering or gliding, either pre-installed or all-moving, possibly capable of deflecting both the angle of attack and the angle of bank, wherein the wing may be equipped with mechanization elements, the console of the monowing is located on top of the body of the product, and the dimensions of the product, including the dimensions and geometry of the wing, correspond to the tested aerodynamic and strength loads in accordance with the weight and dimensions of the transported payload; wherein the head compartment, the payload compartment and the engine compartment are connected to each other at the landing sites.

2. The product according to paragraph 1, characterized in that the monowing console is located below the body of the product.

3. The product according to paragraph 1, characterized in that it has 2 monowings located in the front and rear parts of the product on the upper or lower side of the body or in a combination of upper and lower locations on the body of the product in accordance with its aerodynamic and weight characteristics, while it is possible to use two monowings that differ in area to improve the aerodynamic characteristics of the product.

4. The product according to paragraph 1, characterized in that it has 4 monowings located in the front and rear parts of the body above and below the product in accordance with its aerodynamic and weight characteristics, while possibly differing in pairs in area, to improve the aerodynamic characteristics of the product.

5. The product according to paragraph 1, characterized in that it has two cantilever wings coaxially located in a horizontal plane on the upper or lower side of the product body in accordance with its aerodynamic and weight characteristics, while the wings can rotate both in the angle of attack and in the angle of bank, both synchronously and asynchronously (independently of each other).

6. The product according to paragraph 1, characterized in that it has four cantilever wings, arranged in pairs coaxially in a horizontal plane in the front and rear parts of the body on the upper or lower side of the body, or in a combination of upper and lower arrangement on the body of the product in accordance with its aerodynamic and weight characteristics, wherein the wings can rotate both in the angle of attack and in the angle of bank, both synchronously and asynchronously (independently of each other), and also differ in pairs in area to improve the aerodynamic characteristics of the product.

7. The product according to paragraph 1, characterized in that it has eight cantilever wings, coaxially arranged in pairs in a horizontal plane, located in the front and rear parts of the body on the upper or lower side of the product in accordance with its aerodynamic and weight characteristics, wherein the wings can rotate both in the angle of attack and in the angle of bank, both synchronously and asynchronously (independently of each other), and also differ in pairs in area, to improve the aerodynamic characteristics of the product.

8. A product according to any of paragraphs 1-7, characterized in that the engine can be equipped with coaxial propellers, and the direction of their rotation is regulated by a gearbox.

9. An article according to any one of paragraphs 1-7, characterized in that the engine compartment is equipped with a brushless electric motor, or an electric rocket engine (ERE), or a liquid rocket engine (LRE), or a solid rocket engine (SRE), or a turbojet engine (TRE), or an air-breathing engine (ABBE), or a cryogenic rocket engine, or an internal combustion engine (ICE) with a propeller, providing thrust in accordance with the aerodynamic and weight characteristics of the article.

10. An article according to any of paragraphs 1-7, characterized in that a “propeller-in-ring” (PIR) assembly can be used for the propeller-motor group, and in order to increase the rigidity of the structure, the ring can be attached to the body using additional rigidly fixed rods.

11. An article according to any one of paragraphs 1-7, characterized in that control and correction of the trajectory of movement to the destination is carried out using another navigation and control system known from the prior art, including a laser, thermal imaging, crate system, or a visual detection system through the use of artificial intelligence (AI), which ensures the fixation of the landing point with subsequent movement to it, or control and correction of the trajectory are carried out using an aircraft carrier through feedback with its navigation, control and monitoring systems.

12. The product according to paragraph 11, characterized in that the product is controlled by an operator from a stationary post using telemetry data or a visual control system in the form of cameras for piloting the product.

13. A method for delivering a product to its destination, implemented through the use of a carrier aircraft with the product secured on an external sling, or in a cassette device secured on the external sling of the carrier aircraft, or in the cargo compartment of the carrier aircraft, or in a cassette device secured in the cargo compartment of the carrier aircraft, and its automatic release at the moment the carrier aircraft enters the separation point with the product, located at a distance from the target location equal to the product's flight distance.

14. The method according to paragraph 13, characterized in that the product is launched from a stationary or mobile catapult-type launcher located at the distance of the product’s flight to the area where the designated target is located.